公开(公告)号：US20210130001A1

公开(公告)日：2021-05-06

申请号：US17081193

申请日：2020-10-27

Applicant: Airbus Operations SAS

Inventor： Julien Allain ,  Stéphane Dida ,  Jérome Colmagro ,  Olivier Dubois ,  Julien Moulis ,  Jacky Puech ,  Laurent Lafont

IPC: B64D27/26 ,  B64F5/10 ,  F16B5/08

Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.

公开(公告)号：US11572184B2

公开(公告)日：2023-02-07

申请号：US16878006

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas Deforet ,  Rémi Lansiaux ,  Olivier Dubois ,  Jacky Puech

IPC: B64D27/26

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall that has a front face, and a front engine attachment having a beam that is fixed against the front face and to which is fixed, on either side of a median plane, a rod system, wherein each rod system is fixed to the beam in an articulated manner by at least one first connection point, and is configured to be fixed to a front part of the engine in an articulated manner by at least one second connection point. Such a front engine attachment system thus has rod systems having two rods, allowing the shape of the rods and the shape of the beam to be simplified.

公开(公告)号：US11518531B2

公开(公告)日：2022-12-06

申请号：US16733783

申请日：2020-01-03

Applicant: Airbus Operations SAS

Inventor： Jacky Puech ,  Thomas Deforet ,  Julien Cayssials

IPC: B64D27/26 ,  B64F5/10

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.

公开(公告)号：US11807373B2

公开(公告)日：2023-11-07

申请号：US17081193

申请日：2020-10-27

Applicant: Airbus Operations SAS

Inventor： Julien Allain ,  Stéphane Dida ,  Jérome Colmagro ,  Olivier Dubois ,  Julien Moulis ,  Jacky Puech ,  Laurent Lafont

IPC: B64D27/26 ,  B64F5/10 ,  F16B5/08

CPC classification number: B64D27/26 ,  B64F5/10 ,  F16B5/08 ,  B64D2027/266

Abstract: The pylon, intended to support a flying vehicle engine, includes a primary structure formed by at least one longeron and one panel, the panel including at least one end part provided with a notch, the longeron being provided with an end adapted to be positioned in the notch, the panel and the longeron being assembled by welding a part of the end to a part of the notch. A welded primary structure enables minimization of the blanks of parts associated with the longerons and with the panels by avoiding having recourse to the production of edges.

公开(公告)号：US11542025B2

公开(公告)日：2023-01-03

申请号：US17407251

申请日：2021-08-20

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Thomas Deforet ,  Jacky Puech

IPC: B64D27/26

Abstract: A propulsion assembly including a primary structure of a pylon having right and left extensions projecting with respect to right and left lateral panels of the primary structure and also right and left brackets, each having a first flank connected to the right or left lateral panel of the primary structure and a second flank pressed against the right or left extension, a front engine mount having first and second links, each connected to an engine and directly to the front transverse reinforcement by a first or second reinforcement connection pin passing through the right or left extension and the second flank of the right or left bracket.

公开(公告)号：US11518534B2

公开(公告)日：2022-12-06

申请号：US16878034

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas Deforet ,  Rémi Lansiaux ,  Olivier Dubois ,  Anthony Mertes ,  Jacky Puech

IPC: B64D27/26

Abstract: A front engine attachment system for an engine of an aircraft, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam, which is fastened to the front face and to which a link rod is fastened on either side of a median plane. Each link rod is fastened to the beam in an articulated manner by at least one first connection point and is configured to be fastened to the engine in an articulated manner by at least one second connection point. The beam is made up of front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate.

公开(公告)号：US11518533B2

公开(公告)日：2022-12-06

申请号：US16878015

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas Deforet ,  Rémi Lansiaux ,  Olivier Dubois ,  Jacky Puech

IPC: B64D27/26

Abstract: A front engine attachment system for an aircraft engine, the front engine attachment system having an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam has front, intermediate and rear plates. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. The intermediate plate is disposed between the front plate and the rear plate. Each link-rod system is fastened to the intermediate plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

公开(公告)号：US11975856B2

公开(公告)日：2024-05-07

申请号：US17756554

申请日：2020-11-16

Applicant: Airbus Operations SAS

Inventor： Michael Berjot ,  Jacky Puech ,  Rémi Lansiaux

IPC: B64D27/40 ,  B64D27/18

CPC classification number: B64D27/40 ,  B64D27/18

Abstract: A front engine attachment system for an engine of an aircraft. An engine pylon has a frontal rib with a front engine attachment with a first link rod which is fixed directly to the frontal rib by two connecting points. A second link rod is provided which has a first end fixed to the first link rod by a connecting point. The first link rod is fixed directly to an engine casing by at least two connecting points and a second end of the second link rod is fixed to the engine casing by a third connecting point. The first link rod may be made up of two adjoining plates that are fixed together. Also, an aircraft with such a front engine attachment system.

公开(公告)号：US11535389B2

公开(公告)日：2022-12-27

申请号：US16878011

申请日：2020-05-19

Applicant: Airbus Operations SAS

Inventor： Thomas Deforet ,  Rémi Lansiaux ,  Olivier Dubois ,  Jacky Puech

IPC: B64D27/26

Abstract: A front engine attachment system for an engine of an aircraft. The front engine attachment system has an engine pylon having, in its front part, a frontal part having an attachment wall with a front face, and a front engine attachment having a beam fastened to the front face and to which a link-rod system is fastened on either side of a median plane. The beam is made up of a front plate and a rear plate that are fastened together in a removable manner. The rear plate is pressed against the front face. The front plate is disposed in front of the rear plate. Each link-rod system is fastened to the rear plate in an articulated manner by at least one first connection point and is configured to be fastened to a front part of the engine in an articulated manner by at least one second connection point.

公开(公告)号：US11434015B2

公开(公告)日：2022-09-06

申请号：US16733691

申请日：2020-01-03

Applicant: Airbus Operations SAS

Inventor： Jacky Puech ,  Thomas Deforet ,  Julien Cayssials

IPC: B64D27/26 ,  B64F5/10

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove in such a manner as to immobilize the shear pin in translation.